Capsule aerodynamics and shock-wave boundary layer interaction (SBLI) in supersonic and transonic flow

Abstract

Static force and moment measurements are performed on the MarcoPolo-R aero shape in the trisonic wind tunnel TMK. The static stability behaviour of the capsule is characterized in the Mach number range $$0.5\le M\le 3.5$$ 0.5 ≤ M ≤ 3.5 reproducing the Mach and Reynolds conditions of the flight trajectory in the supersonic regime. An aerodynamic database is built based on the experimental results. The flow structure around the capsule is visualised in supersonic tests by means of schlieren imaging. Under certain conditions, development of a complex shock system on the leeward side of the inclined capsule is observed. Oil film technique is used to visualise boundary layer phenomena in connection to this shock system. Numerical simulations with the DLR TAU code are performed to support the interpretation of the flow phenomena under these conditions. Graphical abstract Schlieren imaging visualisation of density gradients in supersonic flow. Depending on the test conditions and angle of incidence, a complex shock system is observed on the leeward side of the inclined capsule. Analysis of the shock structure and its impact on aerodynamic coefficients is one subject of the present investigation.

Wave Drag Coefficient of Elliptical Forebody Shapes

“…where 𝑐 𝑣 is the air specific heat at constant volume (Anderson, 1995). Exact analytical solutions of the complete Navier-Stokes equations exist for only a few very specialized cases.…”

“…Instead, the equations are frequently simplified by making appropriate approximations about the flow. In modern times, exact solutions of the complete Navier-Stokes equations for many practical problems can be obtained numerically, using various techniques of computational fluid dynamics (Anderson, 2017).…”

“…The distribution of pressure and shear stress represent a distributed load over the surface. The net aerodynamic force on the body is due to the net imbalance between these distributed loads as they are integrated over the entire surface (Anderson, 2017).…”

“…Every study of supersonic flow has to contain calculation of the shape and the strength of shock waves. The shape of the shock wave and complete flow field between the shock and the body depend on upstream Mach number and size and shape of the body (Anderson, 2017).…”